CN106802247A - A kind of composite rear fatigue and defect tolerance experimental rig - Google Patents
A kind of composite rear fatigue and defect tolerance experimental rig Download PDFInfo
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- CN106802247A CN106802247A CN201510844391.XA CN201510844391A CN106802247A CN 106802247 A CN106802247 A CN 106802247A CN 201510844391 A CN201510844391 A CN 201510844391A CN 106802247 A CN106802247 A CN 106802247A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
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Abstract
A kind of composite rear fatigue and defect tolerance experimental rig are provided, for composite rear fatigue and defect tolerance experiment, carrying out the experiment of composite rear defect tolerance using apparatus of the present invention can fully verify its performance and obtain the defect tolerance life-span, background technology can be overcome to determine the organism safe life-span using computational methods, too conservative safe life can only be given, defect can not be given and hold the sunken life-span, it is impossible to give full play to the deficiencies such as the performance of structure.
Description
Technical field
The invention belongs to helicopter body Structure Fatigue Test Technology, be related to a kind of composite rear fatigue and
Defect tolerance experimental rig.
Background technology
Rear is the complicated critical component in helicopter body structure, and Main Load has mass force, tail-rotor thrust
And the aerodynamic force of horizontal tail, vertical fin, its fatigue stress level is apparently higher than middle fuselage and the fatigue stress of head
Level, fatigue life in the general life-span by rear of body replaces.Load that is complicated due to planform, bearing
Lotus is serious, and weight requirement is as far as possible light, therefore it provides accurate fatigue test examination environment, is tried
Test examination acquisition fatigue life and weak part is most important.
Background technology determines the organism safe life-span using computational methods, need to ensure that mathematic(al) expectation is substantially high during calculating
In projected life, and need to can only provide too conservative safe life, it is impossible to provide by flight actual measurement checking
Defect holds the sunken life-span, it is impossible to give full play to the performance of structure.
Apparatus of the present invention bonded composite rear structure and Load Characteristics, carry out experiment contour connection condition,
The loading of horizontal tail load, the loading of tail-rotor load, tail boom load designing load, are combined using apparatus of the present invention
The experiment of material rear defect tolerance can fully verify its performance and obtain the defect tolerance life-span.
The content of the invention
The technical problem to be solved in the present invention：A kind of composite rear fatigue and defect tolerance experiment dress are provided
Put, for composite rear fatigue and defect tolerance experiment, composite tail is carried out using apparatus of the present invention
Section defect tolerance is tested and can fully verify its performance and obtain the defect tolerance life-span, and background technology can be overcome to adopt
Determine the organism safe life-span with computational methods, too conservative safe life can only be given, it is impossible to provide defect appearance
Fall into the life-span, it is impossible to give full play to the deficiencies such as the performance of structure.
Technical scheme：A kind of composite rear fatigue and defect tolerance experimental rig, including it is firm
Property heavy frame, connecting plate, changeover portion bogusware, tail boom load loads fixture, tail-rotor bogusware, tail-rotor load add
Carry fixture, horizontal tail load loads fixture.Changeover portion bogusware uses aircraft real structure, and one end leads to connecting plate
Bolt connection is crossed, the other end is connected by installation state with rear (testpieces), connected using changeover portion bogusware
Can truer simulated test boundary condition and transmission load.Tail-rotor load loads fixture include tail-rotor bogusware,
The vertical load load bar of tail-rotor horizontal load load bar, tail-rotor.Tail-rotor bogusware bottom and testpieces coupling part
Interface design and installation state consistency, are connected by installation state with rear (testpieces).
Rigid heavy frame by symmetrically arranged bottom vertical beam, base cross members, sidepiece raker beam, rear portion raker beam,
Vertical vertical beam and top cross-bar composition, all load are transmitted during experiment by testpieces, and rigid heavy frame sets
Meter should determine according to test load, be rigid support when should ensure that load is loaded.
Connecting plate is used to connect rigid heavy frame and changeover portion bogusware, and connecting plate is provided with and is adapted to changeover portion bogusware
Hole, hole is generally totally 100 or so, two circles, is bolted together.Connecting plate both sides external sets
There is the hole being adapted to rigid heavy frame annular groove, be fixed on rigid heavy frame by king-bolt.
Tail boom load loads fixture 4 includes right side clamping beam, upper clamp beam, left side clamping beam, bottom folder
Hold beam, loading joint, right side clamping wooden unit, upper clamp wooden unit, left side clamping wooden unit, bottom clamping wood
Block.Right side clamping beam, upper clamp beam, left side clamping beam, bottom clamping beam are using channel-section steel and plate weld
Into girder structure, be respectively equipped with the inside of four beams and right side clamping wooden unit, upper clamp wooden unit, left side
Clamping wooden unit, bottom clamp the groove of wooden unit gabarit cuboid size fit, right side clamping wooden unit, top
Clamping wooden unit, left side clamping wooden unit, bottom clamping wooden unit inner profile surface size and testpieces connecting portion curved surface
External shape fits.The face that the clamping beam of four direction is engaged is respectively equipped with the hole of adaptation, is bolted solid
It is scheduled on together.A loading joint is respectively equipped with by bolt on left side clamping beam, bottom clamping beam, is used for
The loading of tail boom horizontal load and vertical load.
Tail-rotor bogusware upper level load and vertical load loading position are respectively equipped with and are loaded with tail-rotor horizontal load
The double fork ears of " u "-shaped of bar, tail-rotor vertical load load bar monaural piece adaptation, for tail-rotor horizontal load and perpendicular
The loading of straight load.
Horizontal tail load loads fixture include it is upper clamping wooden unit, upper grip block, connection stay bolt, lower clamping wooden unit,
Lower grip block, horizontal tail load loading bearing, horizontal tail load load bar.Upper grip block, lower grip block inner side point
Be not provided with it is upper clamping wooden unit, lower clamping wooden unit gabarit cuboid size fit groove, upper grip block,
Lower grip block inner profile surface size is adapted to testpieces connecting portion curved profile.Upper clamping wooden unit, upper clamping
Plate, lower clamping wooden unit, lower grip block both sides relevant position are provided with the hole run through, and are connected by connecting stay bolt
It is fixed together.There is loading bearing by bolts assemblies on lower grip block, loading bearing is provided with and horizontal tail load
The double fork ears of " u "-shaped of load bar monaural piece adaptation, for the loading of horizontal tail load.
During present invention test, can simulation test piece boundary condition exactly, testing stand stabilization, experimental enviroment is good,
Load fluctuation amount is small, is tested by using apparatus of the present invention, and experiment overall error can be controlled within 3%,
The test data obtained using apparatus of the present invention carries out durability analysis, can fully verify its performance and be lacked
Fall into the tolerance limit life-span.
Brief description of the drawings
Fig. 1 is general structure schematic diagram of the invention.
Fig. 2-4 is partial view of the invention.
Specific embodiment
The present invention is described in further details below.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the present invention is that a kind of composite rear fatigue and defect are held
Limit experimental rig, it is characterised in that including rigid heavy frame 1, connecting plate 2, changeover portion bogusware 3, tail boom
Load loads fixture 4, tail-rotor bogusware 5-1, tail-rotor load loads fixture 5, horizontal tail load loads fixture 6.
Changeover portion bogusware 3 uses aircraft real structure, and one end is bolted with connecting plate 2, and the other end is by dress
Machine state is connected with rear (testpieces), using changeover portion bogusware 3 connection can truer simulated test side
Boundary's condition and transmission load.Tail-rotor load loads fixture 5 includes that tail-rotor bogusware 5-1, tail-rotor horizontal load are loaded
The vertical load load bar 5-3 of bar 5-2, tail-rotor.Tail-rotor bogusware 5-1 bottoms set with testpieces coupling part interface
Meter and installation state consistency, are connected by installation state with rear (testpieces).
Rigid heavy frame 1 by symmetrically arranged bottom vertical beam 1-1, base cross members 1-2, sidepiece raker beam 1-3,
Rear portion raker beam 1-4, vertical vertical beam 1-5 and top cross-bar 1-6 composition, institute is transmitted during experiment by testpieces
The design for having load, rigid heavy frame 1 should determine according to test load, be rigidity when should ensure that load is loaded
Support.
Connecting plate 2 is used to connect rigid heavy frame 1 and changeover portion bogusware 3, and connecting plate 2 is provided with false with changeover portion
The hole of the adaptation of part 3, hole is generally totally 100 or so, two circles, is bolted together.Connecting plate 2
Both sides external is provided with the hole being adapted to the annular groove of rigid heavy frame 1, and rigid heavy frame 1 is fixed on by king-bolt
On.
Tail boom load loads fixture 4 include right side clamping beam 4-1, upper clamp beam 4-2, left side clamping beam 4-3,
Bottom clamping beam 4-4, loading joint 4-5, right side clamping wooden unit 4-6, upper clamp wooden unit 4-7, left side
Clamping wooden unit 4-8, bottom clamp wooden unit 4-9.Right side clamping beam 4-1, upper clamp beam 4-2, left side folder
Beam 4-3, bottom clamping beam 4-4 are held using channel-section steel and the girder structure of plate weld, four inner sides of beam point
It is not provided with and is clamped with right side clamping wooden unit 4-6, upper clamp wooden unit 4-7, left side clamping wooden unit 4-8, bottom
The groove of wooden unit 4-9 gabarit cuboid size fits, right side clamping wooden unit 4-6, upper clamp wooden unit 4-7,
Left side clamps wooden unit 4-8, bottom clamping wooden unit 4-9 inner profile surfaces size and testpieces connecting portion curved profile
Adaptation.The face that the clamping beam of four direction is engaged is respectively equipped with the hole of adaptation, is bolted and is fixed on
Together.A loading joint 4-5 is respectively equipped with by bolt on left side clamping beam 4-3, bottom clamping beam 4-4,
For the loading of tail boom horizontal load and vertical load.
Tail-rotor bogusware 5-1 upper levels load and vertical load loading position are respectively equipped with and tail-rotor horizontal load
The double fork ears of " u "-shaped of the vertical load load bar 5-3 monaurals piece adaptation of load bar 5-2, tail-rotor, for tail-rotor
The loading of horizontal load and vertical load.
Horizontal tail load loads fixture 6 include upper clamping wooden unit 6-1, upper grip block 6-2, connection stay bolt 6-3,
Lower clamping wooden unit 6-4, lower grip block 6-5, horizontal tail load loading bearing 6-6, horizontal tail load load bar 6-7.
Upper grip block 6-2, lower grip block 6-5 inner side are respectively equipped with and upper clamping wooden unit 6-1, lower clamping wooden unit 6-4
The groove of gabarit cuboid size fit, upper grip block 6-2, lower grip block 6-5 inner profile surfaces size and examination
Test part connecting portion curved profile adaptation.Upper clamping wooden unit 6-1, upper grip block 6-2, lower clamping wooden unit 6-4,
Lower grip block 6-5 both sides relevant position is provided with the hole run through, and one is fastened on by connecting stay bolt 6-3
Rise.There are loading bearing 6-6, loading bearing 6-6 to be provided with and carried with horizontal tail by bolts assemblies on lower grip block 6-5
The double fork ears of " u "-shaped of lotus load bar 6-7 monaurals piece adaptation, for the loading of horizontal tail load.
During present invention test, can simulation test piece boundary condition exactly, testing stand stabilization, experimental enviroment is good, carries
Lotus undulate quantity is small, is tested by using apparatus of the present invention, and experiment overall error can be controlled within 3%,
The test data obtained using apparatus of the present invention carries out durability analysis, can fully verify its performance and be lacked
Fall into the tolerance limit life-span.
Claims (6)
1. a kind of composite rear fatigue and defect tolerance experimental rig, it is characterised in that：Described device bag
Include rigid heavy frame (1), connecting plate (2), changeover portion bogusware (3), tail boom load loads fixture (4),
Tail-rotor load loads fixture (5) and horizontal tail load loads fixture (6)；Changeover portion bogusware (3) uses aircraft
Real structure, one end is bolted with connecting plate (2), and the other end is connected by installation state with rear,
Using changeover portion bogusware (3) connection can truer simulated test boundary condition and transmission load；Tail-rotor load
Loads fixture (5) is carried vertically including tail-rotor bogusware (5-1), tail-rotor horizontal load load bar (5-2), tail-rotor
Lotus load bar (5-3), tail-rotor bogusware (5-1) bottom and testpieces coupling part Interface design and installation state
Unanimously, it is connected with rear by installation state.
2. composite rear according to claim 1 fatigue and defect tolerance experimental rig, its feature
It is:Rigid heavy frame (1) is by symmetrically arranged bottom vertical beam (1-1), base cross members (1-2), sidepiece
Raker beam (1-3), rear portion raker beam (1-4), vertical vertical beam (1-5) and top cross-bar (1-6) composition,
All load are transmitted by testpieces during experiment, the design of rigid heavy frame (1) determines according to test load,
It is rigid support when ensureing that load is loaded.
3. composite rear according to claim 1 fatigue and defect tolerance experimental rig, its feature
It is:Connecting plate (2) is for connecting rigid heavy frame (1) and changeover portion bogusware (3), connecting plate (2)
The hole being adapted to changeover portion bogusware (3) is provided with, hole is totally 100 or so, two circle, is bolted one
Rise, connecting plate (2) both sides external is provided with the hole being adapted to rigid heavy frame (1) annular groove, by big spiral shell
Bolt is fixed on rigid heavy frame (1).
4. composite rear according to claim 1 fatigue and defect tolerance experimental rig, its feature
It is that tail boom load loads fixture (4) includes right side clamping beam (4-1), upper clamp beam (4-2), a left side
Side clamping beam (4-3), bottom clamping beam (4-4), loading joint (4-5), right side clamp wooden unit (4-6),
Upper clamp wooden unit (4-7), left side clamp wooden unit (4-8) and bottom clamps wooden unit (4-9), right side clamping
Beam (4-1), upper clamp beam (4-2), left side clamping beam (4-3), bottom clamping beam (4-4) use groove
Steel and the girder structure of plate weld, are respectively equipped with the inside of four clamping beams and clamp wooden unit with right side
(4-6), upper clamp wooden unit (4-7), left side clamp wooden unit (4-8), bottom and clamp wooden unit (4-9) outward
The groove of wide cuboid size fit, right side clamps wooden unit (4-6), upper clamp wooden unit (4-7), a left side
Side clamps wooden unit (4-8) and bottom clamping wooden unit (4-9) inner profile surface size and rear connecting portion curved surface
External shape fits, the face that the clamping beam of four direction is engaged is respectively equipped with the hole of adaptation, is bolted solid
It is scheduled on together, being respectively equipped with one by bolt on left side clamping beam (4-3), bottom clamping beam (4-4) adds
Joint (4-5) is carried, for the loading of tail boom horizontal load and vertical load.
5. composite rear according to claim 1 fatigue and defect tolerance experimental rig, its feature
It is：Tail-rotor bogusware (5-1) upper level load and vertical load loading position are respectively equipped with and tail-rotor level
The double fork ears of " u "-shaped of vertical load load bar (5-3) the monaural piece adaptation of load load bar (5-2), tail-rotor,
For the loading of tail-rotor horizontal load and vertical load.
6. composite rear according to claim 1 fatigue and defect tolerance experimental rig, its feature
It is：Horizontal tail load loads fixture (6) includes upper clamping wooden unit (6-1), upper grip block (6-2), connection
Stay bolt (6-3), lower clamping wooden unit (6-4), lower grip block (6-5), horizontal tail load load bearing (6-6)
With horizontal tail load load bar (6-7), upper grip block (6-2), lower grip block (6-5) inner side be respectively equipped with
Upper clamping wooden unit (6-1), the groove of lower clamping wooden unit (6-4) gabarit cuboid size fit, upper clamping
Plate (6-2), lower grip block (6-5) inner profile surface size are adapted to testpieces connecting portion curved profile, on
Clamping wooden unit (6-1), upper grip block (6-2), lower clamping wooden unit (6-4), lower grip block (6-5) both sides
Relevant position is provided with the hole run through, and is connected and fixed by connecting stay bolt (6-3), lower grip block (6-5)
On have a loading bearing (6-6) by bolts assemblies, loading bearing (6-6) is provided with and horizontal tail load load bar (6-7)
The double fork ears of " u "-shaped of monaural piece adaptation, for the loading of horizontal tail load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510844391.XA CN106802247B (en) | 2015-11-26 | 2015-11-26 | A kind of composite material endpiece fatigue and defect tolerance experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510844391.XA CN106802247B (en) | 2015-11-26 | 2015-11-26 | A kind of composite material endpiece fatigue and defect tolerance experimental rig |
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| Publication Number | Publication Date |
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| CN106802247A true CN106802247A (en) | 2017-06-06 |
| CN106802247B CN106802247B (en) | 2019-03-01 |
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| CN201510844391.XA Active CN106802247B (en) | 2015-11-26 | 2015-11-26 | A kind of composite material endpiece fatigue and defect tolerance experimental rig |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN110778894A (en) * | 2019-11-18 | 2020-02-11 | 五冶集团上海有限公司 | Mounting bracket for camera and lamp |
| CN110793839A (en) * | 2019-10-25 | 2020-02-14 | 中航西飞民用飞机有限责任公司 | Method for testing damage tolerance strength of full-size composite spoiler of airplane |
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| EP2660677A2 (en) * | 2012-01-12 | 2013-11-06 | Bell Helicopter Textron Inc. | System and Method of Measuring and Monitoring Torque in a Rotorcraft Drive System |
| CN104019970A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Testing system for testing fatigue performance of helicopter tail rotor |
| CN104215213A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Tail rotor blade calibrating device |
| CN104697753A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Tail blade fatigue test device |
| CN204495552U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
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2015
- 2015-11-26 CN CN201510844391.XA patent/CN106802247B/en active Active
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| EP2660677A2 (en) * | 2012-01-12 | 2013-11-06 | Bell Helicopter Textron Inc. | System and Method of Measuring and Monitoring Torque in a Rotorcraft Drive System |
| CN104697753A (en) * | 2013-12-04 | 2015-06-10 | 中国直升机设计研究所 | Tail blade fatigue test device |
| CN104019970A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Testing system for testing fatigue performance of helicopter tail rotor |
| CN104215213A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Tail rotor blade calibrating device |
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Non-Patent Citations (1)
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109506908A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test horizontal tail load charger |
| CN109506908B (en) * | 2018-11-09 | 2020-10-23 | 中国直升机设计研究所 | Tail end load loading device for fatigue test of tail section test piece |
| CN110793839A (en) * | 2019-10-25 | 2020-02-14 | 中航西飞民用飞机有限责任公司 | Method for testing damage tolerance strength of full-size composite spoiler of airplane |
| CN110793839B (en) * | 2019-10-25 | 2022-03-15 | 中航西飞民用飞机有限责任公司 | Method for testing damage tolerance strength of full-size composite spoiler of airplane |
| CN110778894A (en) * | 2019-11-18 | 2020-02-11 | 五冶集团上海有限公司 | Mounting bracket for camera and lamp |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106802247B (en) | 2019-03-01 |
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Inventor after: Li Qingrong Inventor after: Bao Ming Inventor after: Deng Wen Inventor after: Zhu Haoyu Inventor before: Fang Liying Inventor before: Bao Ming Inventor before: Deng Wen Inventor before: Zhu Haoyu |